Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/02—Blade-carrying members, e.g. rotors
  • F01D5/08—Heating, heat-insulating or cooling means
  • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
  • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/12—Cooling of plants
  • F02C7/16—Cooling of plants characterised by cooling medium
  • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2240/00—Components
  • F05D2240/10—Stators
  • F05D2240/14—Casings or housings protecting or supporting assemblies within
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2250/00—Geometry
  • F05D2250/20—Three-dimensional
  • F05D2250/23—Three-dimensional prismatic
  • F05D2250/232—Three-dimensional prismatic conical
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2250/00—Geometry
  • F05D2250/30—Arrangement of components
  • F05D2250/32—Arrangement of components according to their shape
  • F05D2250/323—Arrangement of components according to their shape convergent
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/20—Heat transfer, e.g. cooling
  • F05D2260/231—Preventing heat transfer
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• the invention relates to the ventilation of a high pressure turbine rotor.
• turbomachine having an X axis and comprising, from upstream to downstream, a high pressure compressor whose rotor has a downstream cone, a diffuser extended downstream on the side of the X axis by an internal casing disposed radially outside said downstream compressor cone, a combustion chamber disposed radially outside said internal diffuser casing, and a high pressure turbine, the rotor of which is connected to the downstream cone of the compressor by a connecting barrel, the casing internal diffuser and the downstream compressor cone delimiting between them a chamber cavity located downstream of a discharge labyrinth and in which a cooling air circulates from upstream to downstream.
• FIG. 1 Such a turbomachine 1 of axis X is shown in FIG. 1.
• the reference 2 designates the disc of the last stage of the high pressure compressor, which comprises at its periphery blades arranged in front of the inlet of a diffuser 3.
• the rotor of the compressor is extended downstream by a downstream cone 4 disposed radially inside an internal casing 5 extending the radially internal part of the diffuser 3.
• An annular combustion chamber 6 is mounted around the internal casing 5.
• the chamber combustion 6 delivers hot gases to a rectifier, not shown in the drawing, arranged upstream of the first stage of a high pressure turbine, the rotor of which is connected by a connecting barrel 7 to the downstream cone 4, in order to drive in rotation the rotor of the high pressure compressor.
• Reference 8 designates the low pressure shaft which connects a low pressure turbine arranged downstream of the high pressure turbine to a low pressure compressor arranged upstream of the high pressure turbine and optionally to a blower in the case of 'a turbojet engine.
• the internal casing 5 of the diffuser 3 defines, with the internal jacket 10 of the combustion chamber, an annular passage 11 for the flow of the air flow delivered by the diffuser 3 and which is intended for the combustion of fuel in the primary zone of the room of combustion and dilution of the combustion gases in the dilution zone in order to lower the temperature of the hot gases supplied to the high pressure turbine.
• Part of the air flow passing through the annular passage 11 can advantageously be used for cooling the blades of the high pressure turbine.
• the internal casing 5 of the diffuser 3 and the downstream cone 4 of the high pressure compressor define between them an annular cavity 12 located radially under the internal casing 5 downstream of a discharge labyrinth 13 mounted under the diffuser 3 and intended to ensure the sealing between the internal casing 5 and the downstream cone 4 of the rotor of the high pressure compressor.
• a leakage air flow enters the chamber 14 located upstream of the discharge labyrinth 13 under the diffuser 3, through the gap separating the upstream end of the radially inner part of the diffuser 3 and the downstream end of the periphery from the compressor disk 2.
• This air flow flows into the annular cavity 12 via the discharge labyrinth 13 and is used to cool the downstream cone 4 of the compressor rotor, and the upstream faces of the turbine rotor, in particular the flange upstream of the turbine disk, then is discharged into the hot gas stream through the purge cavity located between the rectifier and the turbine rotor.
• the annular cavity 12 has a radial section which widens downstream, and the air flow which circulates therein decreases in speed from upstream to downstream and is subjected to significant heating, linked to the powers generated by the friction of the air on the walls of the internal casing 5. These heatings are all the more important as the friction surfaces of the stator are important, and they can reach a value close to 100 ° C.
• the object of the invention is to decrease the powers generated in the annular cavity 12 in order to decrease the temperature of the cooling air flow which circulates there.
• turbomachine further comprises a stator fairing installed under the internal casing of the diffuser downstream of the discharge labyrinth.
• the radii of the stator in this region are greatly reduced, which leads to a reduction in the friction surfaces of the stator, and a reduction in the powers generated by the friction.
• the cross section of the annular cavity defined by the stator fairing and the downstream cone is substantially constant from upstream to downstream.
• This arrangement allows a substantially uniform speed of the air flow in this annular cavity, and reduces the time of transfer of the air flow in this zone.
• stator fairing and the internal casing of the diffuser delimit between them an annular chamber which separates the annular passage situated around the internal casing of the diffuser, from the annular cavity.
• the temperature in this annular chamber is substantially equal to half the temperature of the two air flows, which makes it possible to reduce the heat exchanges between the two air flows.
• FIG. 1 is a half-section of the part located under the combustion chamber of a turbomachine, according to the prior art.
• FIG. 2 is a half-section of the part located under the combustion chamber of a turbomachine according to the invention.
• FIG. 2 shows the part of a turbomachine according to the invention, located radially inside the combustion chamber 6 downstream of the last stage of a high pressure compressor.
• the compressor disc 2 is extended downstream by a downstream cone 4 connected to the connecting barrel of the rotor of the high pressure turbine.
• the diffuser 3 also comprises an internal casing 5 of flared shape downstream disposed inside the jacket 10 radially inside the combustion chamber 6 and defining with the latter a passage 11 in which the flow of air delivered by the diffuser 3.
• a discharge labyrinth 13 is provided under the diffuser 3 between the internal casing 5 and the downstream cone 4.
• a stator fairing 20 is installed under the internal casing 5 downstream of the discharge labyrinth 13.
• This conical annular passage 21 whose radius decreases from upstream to downstream allows the flow of the leakage flow which passes through the discharge labyrinth 13 towards an enclosure 22 located downstream of the fairing 20, in order to ensure the cooling of the upstream faces of the turbine rotor.
• the fairing 20 and the internal casing 5 of the diffuser 3 delimit a chamber 23 which thermally isolates the main air flow circulating in the passage 11 and the leakage flow circulating in the conical annular passage 21.
• the air contained in this chamber 23 is at an intermediate temperature between that of the main air flow and that of the leak rate.
• stator fairing 20 under the internal casing 5 of the diffuser 3 makes it possible to significantly reduce the friction surfaces of the stator and therefore to reduce the powers generated in the annular passage 21.
• the temperature of the air entering the chamber 22 is reduced by a value which can reach 26 ° C.
• the leakage rate is reduced through the discharge labyrinth 13, so that the temperature of the air in the chamber 22 is equal to the temperature at this location in the absence of the fairing 20, the gain in specific consumption fuel can be estimated at around 0.1%.

Landscapes

• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

Applications Claiming Priority (3)

Publications (2)

Family

ID=29286535

Family Applications (1)

Country Status (7)

Families Citing this family (10)

Family Cites Families (10)

• 2002
  • 2002-05-16 FR FR0206010A patent/FR2839745B1/fr not_active Expired - Lifetime
• 2003
  • 2003-05-16 AU AU2003258763A patent/AU2003258763A1/en not_active Abandoned
  • 2003-05-16 WO PCT/FR2003/001497 patent/WO2003098020A2/fr not_active Ceased
  • 2003-05-16 EP EP03752830.4A patent/EP1504178B1/de not_active Expired - Lifetime
  • 2003-05-16 RU RU2004136856/06A patent/RU2311549C2/ru active
  • 2003-05-16 JP JP2004505519A patent/JP4195692B2/ja not_active Expired - Lifetime
  • 2003-05-16 US US10/513,447 patent/US7036320B2/en not_active Expired - Lifetime

Non-Patent Citations (1)

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